CN102384103A - Airfoil shape for compressor - Google Patents
Airfoil shape for compressor Download PDFInfo
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- CN102384103A CN102384103A CN2011102573201A CN201110257320A CN102384103A CN 102384103 A CN102384103 A CN 102384103A CN 2011102573201 A CN2011102573201 A CN 2011102573201A CN 201110257320 A CN201110257320 A CN 201110257320A CN 102384103 A CN102384103 A CN 102384103A
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- Prior art keywords
- rotor blade
- blade
- rotor
- blade height
- tmax
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/141—Shape, i.e. outer, aerodynamic form
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
- F02C3/06—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/26—Rotors specially for elastic fluids
- F04D29/32—Rotors specially for elastic fluids for axial flow pumps
- F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
- F04D29/324—Blades
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/26—Rotors specially for elastic fluids
- F04D29/32—Rotors specially for elastic fluids for axial flow pumps
- F04D29/38—Blades
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2250/00—Geometry
- F05D2250/70—Shape
- F05D2250/74—Shape given by a set or table of xyz-coordinates
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/96—Preventing, counteracting or reducing vibration or noise
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10S416/00—Fluid reaction surfaces, i.e. impellers
- Y10S416/02—Formulas of curves
Abstract
Devices, systems and methods according to exemplary embodiments provide blades, e.g., as part of a rotor (102) or a stator (106) associated with a turbo machine, with particular shapes to optimize operating characteristics. Among other things, blade thickness as a function of blade height can be tailored to operating characteristics of the turbo machine.
Description
Technical field
The present invention relates generally to the aerofoil profile part, and more specifically, relates to the airfoil shape that in the compressor as the part of gas turbine for example, uses.
Background technique
Compressor is through using mechanical energy to make gas particles quicken the machine with the pressure of final increase compressible fluid (for example gas).Compressor is used for many different application, comprises that operation is used as the initial level of gas turbine engine.In various types of compressors, there are so-called centrifugal compressor and axial compressor; In centrifugal compressor; Mechanical energy with the mode of CENTRIFUGAL ACCELERATING for example through making receded disk impeller (being also referred to as " rotor " sometimes) rotation that transmits compressible fluid come the gas input of compressor is worked, axial compressor the attached rotary drum that many annular aerofoil spares rows (blade) are arranged it on as each grade.The aerofoil profile part that is attached on the rotary drum is being attached to rotation between the fixedly aerofoil profile part row of the similar quantity on the stationary housing.More generally, can think that axial compressor and centrifugal compressor are parts that is called one type of machine of " turbo machine " or " turbine rotating machinery ".
In gas turbine engine, should satisfy many system requirements at each grade place of the flow path section of gas turbine, to satisfy design object.These design objects include but not limited to total improved efficient and aerofoil profile part load capability.For example and never limit the present invention, the blade of compressor stator should be realized being positioned hot service condition and the mechanical movement requirement that a specific order wherein is associated with it.Similarly and also as pure illustrative example, the blade of compressor drum also should be realized being positioned hot service condition and the mechanical movement requirement that a specific order of gas turbine wherein is associated with it.
Particularly, with desirable be to guarantee that the shaping surface of such blade is to make their resonant frequency be tuned to the roadability that is suitable for turbo machine generally.
Summary of the invention
According to device, the system and method for exemplary embodiment the blade of the part of rotor that for example conduct is associated with turbo machine or stator is provided, blade has given shape to optimize roadability.Except other, can make the roadability that adapts to turbo machine as the vane thickness of the function of blade height.
According to an exemplary embodiment; A kind of rotor blade has nominal (nominal) surface profile of the cartesian coordinate X, Y and the Z that are set forth in basic basis such as the table 1; And wherein; X and Y are the distances of representing with millimeter, and they limit each airfoil profile cross section apart from the Z place of representing with millimeter when being connected by level and smooth, continuous arc, and the airfoil profile cross section of Z distance connects smoothly each other and forms complete airfoil shape.
According to another exemplary embodiment; A kind of rotor blade comprises the root portion on the platform that is connected to of platform, rotor blade; And end at the blade surface in the part of tip; Blade surface has the cross section airfoil shape, and wherein, the thickness of rotor blade changes according to the function that three different linear functions are used as the rotor blade height.
According to another exemplary embodiment; A kind of turbo machine comprises transmission shaft, at least one rotor wheel, is installed in a plurality of rotor blades along circumferentially spaced, stator on the rotor wheel; And be attached to a plurality of stator vanes on the stator along circumferentially spaced; Wherein, In these a plurality of rotor blades and a plurality of stator vane at least one further comprises: this in platform, these a plurality of rotor blades and a plurality of stator vane at least one be connected to the root portion on the platform, and end at the blade surface in the part of tip, blade surface has the cross section airfoil shape; Wherein, at least one thickness of this in these a plurality of rotor blades and a plurality of stator vanes changes according to the function that three different linear functions are used as blade height.
Description of drawings
Accompanying drawing shows exemplary embodiment, wherein:
Fig. 1 has described the exemplary axial compressor that can realize therein according to the blade shape of exemplary embodiment;
Fig. 2 has shown the suction side according to the rotor blade of an exemplary embodiment;
Fig. 3 has shown according to the rotor blade of an exemplary embodiment on the pressure side;
Fig. 4 shows the each side that is associated with the coordinate system that is used for limiting according to the track of the point of an exemplary embodiment; And
Fig. 5 is the plotted curve of having described according to an exemplary embodiment as the vane thickness of the function of blade height.
Embodiment
The following detailed description of exemplary embodiment is with reference to accompanying drawing.The identical or similar elements of same reference numerals sign in different figure.And, below describe in detail and do not limit the present invention.On the contrary, scope of the present invention is defined by the following claims.
For to some backgrounds being provided, the brief discussion that is associated with axial compressor is provided at first about follow-up argumentation according to the airfoil shape of exemplary embodiment.In axial compressor, rotor blade applies kinetic energy to air stream, and therefore brings the pressure liter of the hope that strides across compressor.After rotor aerofoil profile part, be stator aerofoil profile part level directly.Rotor aerofoil profile part and stator aerofoil profile part turn to air stream, make air stream speed slack-off (in the corresponding aerofoil profile part framework of reference), and produce the rising of the static pressure of air stream.
Except other desirable aspect of these exemplary embodiments; The structure of aerofoil profile part (and interaction of they and aerofoil profile part on every side); Comprise for example their peripheral edge surface (profile); Confirmed the level and smooth laminar flow between level air stream efficient, aeromechanics property, level and the level, the thermal stress that reduces, in order to effectively transmission air stream between level and the level grade the correlation of enhancing, and the mechanical stress that reduces.Typically, arrange the rotor/stator level more and in the axial flow compressor, pile up, with the exhaust pressure of realization hope and the ratio of inlet pressure.Rotor aerofoil profile part and stator aerofoil profile part can be fixed on rotor wheel or the stator case through suitable attached structure (being commonly referred to " root ", " base portion " or " Dovetail "), have been described below the instance of suitable attached structure.
Fig. 1 shows the exemplary axial compressor 100 that for example is associated with gas-turbine compressor.Mention like top institute, axial compressor typically comprises a plurality of compressor stages, and for example 17 or 18 levels still it will be understood by those skilled in the art that the axial compressor according to exemplary embodiment can comprise any amount of stage and stator stage.The level 100 of the axial compressor shown in Fig. 1 comprises a plurality of rotor blades 102 along circumferentially spaced of being installed on rotor wheel or the rotary drum 104 and is attached to a plurality of stator vanes 106 along circumferentially spaced on the Static Compression engine housing 108.
In the rotor wheel 104 each is attached on the rear propeller shaft 110, and rear propeller shaft 110 is connected on the turbine (not shown) of motor.Rotor blade 102 is arranged in the flow path of axial compressor with stator vane 106.In this exemplary axial compressor, along the direction of the air stream of flow path by arrow 112 indications.To understand, the level 100 of axial compressor only is the example of the various levels of axial compressor, and the shown and level of describing 100 of axial compressor is not intended to limit by any way the present invention.
In Fig. 2 and 3, illustrate in greater detail the rotor blade 102 according to exemplary embodiment, Fig. 2 and 3 has shown the relative side of rotor blade 102.Particularly but do not limit the present invention, can be used in the first order of axial compressor (axial compressor that is for example shown among Fig. 1), promptly near the level of the inlet that is associated with process stream according to such rotor blade 102 of these exemplary embodiments.Particularly, Fig. 2 has described the suction side according to the rotor blade 102 of an exemplary embodiment, and the same rotor blade 102 that Fig. 3 has described to have leading edge (LE) and trailing edge (TE) on the pressure side, as showing about compressor flow path 112.Each rotor blade 102 can for example be provided with the platform 200 and the basically axial entering Dovetail 202 of (or near axially), with rotor wheel 104 on the Dovetail (not shown) that matches of complementary shape be connected.In addition; Each rotor blade 102 comprises rotor blade aerofoil profile part 204; The profile that rotor blade aerofoil profile part 204 has into the general shape of aerofoil profile part at its any section (promptly from aerofoil profile part root 206 to rotator tip 208) will be as below will discussing in more detail.
In order to limit airfoil shape, the set or the track of the point in the space is provided below in the table 1 according to the rotor blade aerofoil profile part 204 of exemplary embodiment.Can see that the exemplary rotor blade 102 in Fig. 2 and 3 has 16 section lines, but those skilled in the art will approve, can limit any amount of cross section.This collection or the track intention of point satisfies with rotor blade 102 will be used for the cross section requirement that wherein section or a plurality of section are associated, and feasiblely can make this cross section.This track of point also is intended to satisfy for the regulation of the expectation of stage efficiency and the thermal stress and the mechanical stress of reduction.Obtain track a little through emulation: iteration between aerodynamic load and mechanical load, and make that the compressor that designs according to exemplary embodiment can be with efficient, safety and smooth mode operation.
More specifically, this track defines the rotor blade airfoil profile according to exemplary embodiment, and can comprise about the spin axis of motor and the set of the point that limits.For example, definable comes with reference to the point in the track with the cartesian coordinate system that uses X, Y and Z value.The X that cartesian coordinate system is correlated with having quadrature, Y and Z axle.According to this exemplary embodiment, the X axle is arranged to be parallel to the center line of motor, that kind that goes out as shown in Figure 4.Positive X coordinate figure thereby vertically towards the rear portion is for example towards the exhaust end of axial compressor.Positive Y coordinate figure is oriented along circumferentially deferring to motor and is rotated counterclockwise direction.Positive Z coordinate figure is oriented radially outwards towards the tip of aerofoil profile part 204, and promptly the edge is towards the direction of the quiet housing 108 of compressor.Be merely the purpose of reference, set up along piling up the point 0 that axis passes the junction of aerofoil profile part 204 and platform 200, that kind that goes out as shown in Figure 4.In the exemplary embodiment according to the aerofoil profile part of these exemplary embodiments, the Z coordinate of the table 1 below point 0 is defined as wherein is in the baseline cross-section of 416.97 millimeters (these are the intended distances apart from the setting of motor or rotor centerline).
The table 1 that defines according to the point on the surface of the rotor blade 102 of exemplary embodiment is provided below.
Table 1
Cross section 1 Z=416.97
Cross section 2 Z=424.59
Cross section 3 Z=432.21
Cross section 4 Z=449.99
Cross section 5 Z=467.77
Cross section 6 Z=493.17
Cross section 7 Z=518.57
Cross section 8 Z=543.97
Cross section 9 Z=569.37
Cross section 10 Z=589.69
Cross section 11 Z=610.01
Cross section 12 Z=622.71
Cross section 13 Z=627.79
Cross section 14 Z=632.87
Cross section 15 Z=642.93
Cross section 16 Z=648.01
According to exemplary embodiment; Table 1 through according to the point of top elaboration is made rotor blade 102; The thickness of rotor blade 102 changes along blade height continuously; So that the vibration frequency with the movements of rotor blade 102 is moved, for example to improve the plan boundary that is associated with fatigue.For example in the plotted curve of Fig. 5, can see this variation of thickness.In Fig. 5; Near about 2.21% (promptly just having exceeded the blade fillet radius) platform 200, that originate in blade height of rotor blade in about 60% first area of blade height, can describe by following linear function according to the maximum ga(u)ge of the rotor blade 102 of this exemplary embodiment:
Tmax=-0.8646*h+1.1087 (wherein, h is a blade height percentage) is that the maximum ga(u)ge of rotor blade 102 changes according to following linear function in 60% to 80% the follow-up zone of rotor blade height in scope:
Tmax=-1.0209*h+1.2058 (wherein h is a blade height percentage)
In scope is that the maximum ga(u)ge of rotor blade 102 changes according to following linear function in the follow-up zone of 80% to 100% free end of blade (promptly to) of blade height:
Tmax=-0.7618*h+0.9985 (wherein, h is a blade height percentage)
Thereby; (wherein function 500 has been described the rotor blade thickness as the function of blade height of an exemplary embodiment at the plotted curve of Fig. 5; And function 502 has been described the equal number of reference design) in can see; Exemplary embodiment provides about preceding thicker rotor blade of 75% (function intersects herein) of penetrating blade height, and rotor blade thinner for reference design is provided then.But will understand, these exemplary functions are illustrative, and will expect that some of the point of setting forth in the table 1 change, as will be described below.
It will be understood by those skilled in the art that table 1 provides enough data to come intactly to limit the shape according to the aerofoil profile part 204 of exemplary embodiment.For example, through limiting, can confirm that the length along this aerofoil profile part of rotor blade aerofoil profile part 204 is in the section of outline of each Z distance along perpendicular to the Z direction on X, Y plane X and Y coordinate figure at the select location place.Through connecting X and Y value with level and smooth, continuous arc, fixing aerofoil profile part 204 at each each section of outline apart from the Z place.On being connected to contiguous section of outline each other smoothly, confirm at airfoil profile apart from each surface location between the Z, thus the profile of formation aerofoil profile part 204.The airfoil profile according to exemplary embodiment of value representation under environmental condition, inoperative situation or non-hot situation of in table 1, setting forth above, and be to be directed against uncoated aerofoil profile part.
The tabular value that in table 1, provides generates and is shown as two decimal places, to confirm the profile of aerofoil profile part 204.Typical manufacturing tolerances and coating that existence should be considered in the TP of aerofoil profile part.Therefore, the value that it will be understood by those skilled in the art that the profile that provides in the table 1 is to nominal aerofoil profile part 204.Therefore will understand, the actual value that these exemplary embodiments comprised is not limited to the exact value of demonstration in the table 1, but opposite, and these actual values intentions comprise certain value scope on every side of those values of stipulating in the table.
For example, the value that is comprised should be the typical manufacturing tolerances of plus or minus, and/or any coating thickness that on aerofoil profile part 204, uses of plus or minus.Therefore, along airfoil profile along perpendicular to the direction of any surface location approximately+/-distance of 1.0mm defines according to the rotor blade aerofoil profile part design of these exemplary embodiments and the airfoil profile envelope of compressor.In other words; According to exemplary embodiment; Along airfoil profile along perpendicular to the direction of any surface location approximately+/-1.0mm and preferably approximately+/-distance of 0.5mm defines the scope that is in the difference between the lip-deep measured point of actual aerofoil profile part in nominal low temperature or room temperature, and at the ideal position of those points at uniform temp place.
In addition, it will be understood by those skilled in the art that according to the shape of the aerofoil profile part 204 of these exemplary embodiments and also will become the shape after their being heated when being arranged to gas turbine engine operation from their alteration of form of low temperature or room temperature manufacturing.When aerofoil profile part 204 heating in use, the variation of the low temperature that stress and temperature will cause describing in the table 1 or the X of room temperature point, Y, Z value.Thereby exemplary embodiment has further been conceived and has been comprised the variation that is associated in the heating of normal operation period with aerofoil profile part 204.
Be applied as can be used as first order rotor shapes through the aerofoil profile part that exemplary embodiment embodied.Set forth the coordinate figure of X, Y and Z coordinate with millimeter (being unit), but when value is changed rightly, can use other dimensional units.These values do not comprise the radius area of platform.
Above-described exemplary embodiment intention is explained the present invention and unrestricted the present invention in every respect.Thereby the present invention can be in detailed realization many modification of obtaining of the description that comprises in can be according to this paper of capable field technique personnel.All such variants and modifications are counted as and are in the scope of the present invention and spirit that is defined by the following claims.The element that uses in the application's the description, action or indication are not to be understood that for being crucial or essential for the present invention, only if describe so clearly.And as used herein, article " " intention comprises one or more projects.
Claims (10)
1. rotor blade; It has the nominal surface profile of the cartesian coordinate X, Y and the Z that are set forth in basic basis such as the table 1; And wherein; X and Y are the distances of representing with millimeter, and they limit each airfoil profile cross section apart from the Z place of representing with millimeter when being connected by level and smooth, continuous arc, and the said airfoil profile cross section of said Z distance connects smoothly each other and forms complete airfoil shape.
2. rotor blade according to claim 1; It is characterized in that, basic according to the said nominal surface profile like the cartesian coordinate X, Y and the Z that are set forth in the table 1 comprise along perpendicular to the direction on any surface of said complete airfoil shape+/-point in the 1mm.
3. rotor blade according to claim 1 is characterized in that, about 2.21% of the blade height that originates in of said rotor blade is described by following formula up to about 60% maximum ga(u)ge (Tmax) of rotor blade height:
Tmax=-0.8646*h+1.1087, wherein, h is a blade height percentage; Wherein, said rotor blade is that said maximum ga(u)ge in about 60% to about 80% the first follow-up zone of said rotor blade height is described by following formula in scope:
Tmax=-1.0209*h+1.2058, wherein h is a blade height percentage; And
Wherein, said rotor blade is that said maximum ga(u)ge in 80% to 100% the second follow-up zone of said rotor blade height is described by following formula in scope:
Tmax=-0.7618*h+0.9985, wherein h is a blade height percentage.
4. rotor blade comprises:
Platform;
Said rotor blade be connected to the root portion on the said platform; And
End at the blade surface in the part of tip, said blade surface has the cross section airfoil shape,
Wherein, the thickness of said rotor blade changes according to the function that three different linear functions are used as the rotor blade height.
5. rotor blade according to claim 4; It is characterized in that about 2.21% of the blade height that originates in of said rotor blade is described by first linear function in said three linear functions up to about 60% maximum ga(u)ge (Tmax) of rotor blade height:
Tmax=-0.8646*h+1.1087, wherein, h is a blade height percentage; Wherein, said rotor blade is that said maximum ga(u)ge in about 60% to about 80% the first follow-up zone of said rotor blade height is described by second linear function in said three linear functions in scope:
Tmax=-1.0209*h+1.2058, wherein h is a blade height percentage; And wherein, said rotor blade be that said maximum ga(u)ge in 80% to 100% the second follow-up zone of said rotor blade height is described by the 3rd linear function in said three linear functions in scope:
Tmax=-0.7618*h+0.9985, wherein h is a blade height percentage.
6. rotor blade according to claim 4; It is characterized in that; Said rotor blade has the nominal surface profile of the cartesian coordinate X, Y and the Z that are set forth in basic basis such as the table 1, and wherein, X and Y are the distances of representing with millimeter; They limit each airfoil profile cross section apart from the Z place of representing with millimeter when being connected by level and smooth, continuous arc, the said airfoil profile cross section of said Z distance connects smoothly each other and forms complete airfoil shape.
7. rotor blade according to claim 6; It is characterized in that, basic according to the said nominal surface profile like the cartesian coordinate X, Y and the Z that are set forth in the table 1 comprise along perpendicular to the direction on any surface of said complete airfoil shape+/-point in the 1mm.
8. turbo machine comprises:
Transmission shaft;
At least one rotor wheel;
Be installed in a plurality of rotor blades on the said rotor wheel along circumferentially spaced;
Stator; And
Be attached to a plurality of stator vanes on the said stator along circumferentially spaced,
Wherein, at least one in said a plurality of rotor blade and a plurality of stator vane further comprises:
Platform;
In said a plurality of rotor blade and a plurality of stator vane said at least one be connected to the root portion on the said platform; And
End at the blade surface in the part of tip, said blade surface has the cross section airfoil shape,
Wherein, said at least one the thickness in said a plurality of rotor blade and a plurality of stator vanes changes according to the function that three different linear functions are used as blade height.
9. turbo machine according to claim 8; It is characterized in that said at least one about 2.21% of the blade height that originates in said a plurality of rotor blades and a plurality of stator vane is described by first linear function in said three linear functions up to about 60% maximum ga(u)ge (Tmax) of blade height:
Tmax=-0.8646*h+1.1087, wherein, h is a blade height percentage; Wherein, in said a plurality of rotor blade and a plurality of stator vane said at least one be that said maximum ga(u)ge in about 60% to about 80% the first follow-up zone of said blade height is described by second linear function in said three linear functions in scope:
Tmax=-1.0209*h+1.2058, wherein h is a blade height percentage; And wherein, in said a plurality of rotor blades and a plurality of stator vane said at least one be that said maximum ga(u)ge in 80% to 100% the second follow-up zone of said blade height is described by the 3rd linear function in said three linear functions in scope:
Tmax=-0.7618*h+0.9985, wherein h is a blade height percentage.
10. turbo machine according to claim 8; It is characterized in that; In said a plurality of rotor blade and a plurality of stator vane said at least one have the nominal surface profile of the cartesian coordinate X, Y and the Z that are set forth in basic basis such as the table 1; And wherein; X and Y are the distances of representing with millimeter, and they limit each airfoil profile cross section apart from the Z place of representing with millimeter when being connected by level and smooth, continuous arc, and the said airfoil profile cross section of said Z distance connects smoothly each other and forms complete airfoil shape; And wherein, basic according to the said nominal surface profile like the cartesian coordinate X, Y and the Z that are set forth in the table 1 comprise along perpendicular to the direction on any surface of said complete airfoil shape+/-point in the 1mm.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| ITCO2010A000045 | 2010-08-25 | ||
| ITCO2010A000045A IT1401661B1 (en) | 2010-08-25 | 2010-08-25 | FORM OF AODINAMIC PROFILE BY COMPRESSOR. |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN102384103A true CN102384103A (en) | 2012-03-21 |
| CN102384103B CN102384103B (en) | 2015-12-16 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201110257320.1A Expired - Fee Related CN102384103B (en) | 2010-08-25 | 2011-08-25 | For the airfoil shape of compressor |
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| Country | Link |
|---|---|
| US (1) | US8882456B2 (en) |
| EP (1) | EP2423436B1 (en) |
| JP (1) | JP6055172B2 (en) |
| KR (1) | KR101819240B1 (en) |
| CN (1) | CN102384103B (en) |
| CA (1) | CA2749488A1 (en) |
| IT (1) | IT1401661B1 (en) |
| RU (1) | RU2581501C2 (en) |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103511355A (en) * | 2012-06-19 | 2014-01-15 | 通用电气公司 | Airfoil shape for use in compressor |
| CN104154036A (en) * | 2013-05-14 | 2014-11-19 | 曼柴油机和涡轮机欧洲股份公司 | Rotor blade for a compressor and compressor having such a rotor blade |
| CN103511341B (en) * | 2012-06-19 | 2018-02-23 | 通用电气公司 | Aerofoil profile product for compressor reducer |
Families Citing this family (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US9297259B2 (en) * | 2012-06-14 | 2016-03-29 | Alstom Technology | Compressor blade |
| US9845684B2 (en) * | 2014-11-25 | 2017-12-19 | Pratt & Whitney Canada Corp. | Airfoil with stepped spanwise thickness distribution |
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Also Published As
| Publication number | Publication date |
|---|---|
| IT1401661B1 (en) | 2013-08-02 |
| EP2423436A3 (en) | 2014-06-11 |
| US8882456B2 (en) | 2014-11-11 |
| RU2011135181A (en) | 2013-02-27 |
| EP2423436A2 (en) | 2012-02-29 |
| CN102384103B (en) | 2015-12-16 |
| ITCO20100045A1 (en) | 2012-02-26 |
| KR101819240B1 (en) | 2018-01-16 |
| CA2749488A1 (en) | 2012-02-25 |
| JP2012047175A (en) | 2012-03-08 |
| JP6055172B2 (en) | 2016-12-27 |
| KR20120019399A (en) | 2012-03-06 |
| EP2423436B1 (en) | 2016-06-01 |
| US20120051901A1 (en) | 2012-03-01 |
| RU2581501C2 (en) | 2016-04-20 |
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